Abstract: A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.

Abstract: A rocket engine system having a heating system configured to heat an oxidizer; a combustion section having a flow path from an upstream inlet section through a restricted throat section to a downstream outlet section, the combustion section configured to accelerate the heated oxidizer as an oxidizer stream within the flow path in response to flow dynamics to supersonic speed; and a fuel system configured to introduce a fuel into the flow path to mix supersonically with the heated oxidizer to define a combined fuel and oxidizer stream at a first supersonic speed. The combined fuel and oxidizer stream undergoes a deflagration to denotation transition in the combustion section defined by an oblique shock wave and a normal shock wave that interact to achieve a standing detonation wave generally at an upstream portion of the restricted throat section configured such that combustion exits the downstream outlet section to provide thrust.

Abstract: A thrust reverser includes a diverter configured to divert at least a portion of an air flow from a nacelle and a cowl movable relative to an outer fixed structure of the thrust reverser. The thrust reverser further includes at least one rotatably hinged flap. The cowl configured to move from a closure position in which it provides aerodynamic continuity of the nacelle with the flap and covers the diverter. The flap is movable from a retracted position to an opening position in which it opens a passage in the nacelle and uncovers the diverter. The flap obstructs a portion of an annular channel of the nacelle when in the opening position. The thrust reverser also includes a cable-pulley system for driving the flap. The cable-pulley system includes at least one cable associated with at least one pulley to connect the flap to the thrust reverser.

Abstract: An annular or semi-annular acoustic attenuation structure includes an inner skin and an outer skin, defining between them an annular or semi-annular volume, and a plurality of partitions extending in the space in a radial direction perpendicular to the inner and outer skins and in a circumferential direction. The inner and outer skins and the partitions are made of composite material including a fibrous reinforcement densified by a matrix. The fibrous reinforcement of each partition includes yarns or fibers extending into the fibrous reinforcement of at least one of the inner or outer skins.

Abstract: A thrust reverser system for jet aircraft comprising an exhaust tailpipe mounted to the turbine engine aft turbine flange and two clamshell doors, actuators and a locking system to prevent inadvertent deployment of the clamshell doors in-flight. Two improved design clamshell doors configurations, either one or a combination of both, mounted on either side of the top and bottom of the exhaust tailpipe, fitted with two patented design actuators mounted one on each side of the external sides of the tailpipe between the clamshell doors and the tailpipe, possibly in a depression in the tailpipe called blister, assuming them to be hydraulic actuators for discussion purposes. The actuators drive the clamshell doors using improved floating linkages loosely pivoted to the exterior of the exhaust tailpipe.

Abstract: An architecture for controlling and/or monitoring at least one actuator of a mobile cowl of a thrust reverser equipping a nacelle, the actuator being driven by at least one engine, includes at least one engine sensor to provide its control according to instructions, the architecture including an electronic control system to process at least one piece of information generated by the engine sensor and to calculate, using at least this same piece of information, the position of the mobile cowl of the thrust reverser.

Abstract: The subject matter of this specification can be embodied in, among other things, a thrust reverser tertiary lock apparatus that includes a probe affixed to an aircraft engine frame and having a shaft having a barb at a first end and configurable to a first configuration and a second configuration, and a receiver affixed to a thrust reverser transcowl slider configured to accommodate the barb and having an end wall with an aperture defined therein, the aperture shaped to permit escapement of the barb in the first configuration and prevent escapement of the barb in the second configuration.

Abstract: A method of operating a reverse thrust system of an aircraft engine, the method comprising: receiving a status signal indicative that the aircraft is on-ground or in-flight; and upon detecting that the aircraft is on-ground, overriding a protection module such that the reverse thrust system is operable regardless of the protection module being in an active state or in a disabled state, the protection module causing, absent the overriding, the reverse thrust system to be inoperable when in the active state. An aircraft comprising: an engine including a reverse thrust system; a thrust control input device configured for generating an input signal indicative of a reverse thrust demand; at least one sensor configured for generating at least one status signal indicative of the aircraft being in-flight or on-ground; and a control system electronically connected with the at least one sensor, the thrust control input device and the reverse thrust system.

Abstract: A latch assembly includes a housing including a first housing portion and a second portion including. The latch assembly further includes a first latch member disposed within the first housing portion and configured for translation along the latch axis. The first latch member includes at least two rotatable arms configured to rotate between an arm retracted position and an arm extended position in which the at least two rotatable arms extend in a first direction away from the latch axis. The latch assembly further includes a second latch member disposed within the second housing portion and configured for translation along the latch axis. The second latch member includes a second latch member body including a base portion and at least one axially extending portion extending from the base portion in a second direction toward the interior surface of the lateral wall.

Abstract: A nacelle may comprise a fixed structure and a translating structure configured to translate relative to the fixed structure. A first drive system may be operationally coupled to the translating structure. The drive system may comprise a primary actuator coupled to the fixed structure and including a primary rod and a primary gear rotationally coupled to the primary rod, a torque shaft rotationally coupled to the primary gear, and a secondary actuator operationally coupled to the primary actuator via the torque shaft.

Abstract: A thrust reverser includes a frame, a track disposed on the frame, a carrier operatively coupled to the track, and a first reverser door operatively coupled to the carrier. The first reverser door is movable relative to the frame. The first reverser door is configured to move to a first position in response to the carrier moving with respect to the track in a first direction, and move to a second position in response to the carrier moving with respect to the track in a second direction.

Abstract: A power generation assembly for a weapon system converts waste energy from a firing event to electric power. The power generation assembly directs expanding burning propellant gasses within the weapon system into a turbine array to generate electric current. The electric current is rectified to trickle charge a battery bank which then powers the weapon system.

Abstract: An interspatial blocker for a thrust reverser system of a turbofan engine, and a thrust reverser system and a turbofan engine incorporating the same. The interspatial blocker includes a first and second flap that rotate from a stored position to a blocking position, and a leading-edge structure rotatably coupling the first flap to the second flap. The leading-edge structure is set up to be installed in a fan nacelle of a turbofan engine in a substantially radial orientation such that the first flap rotates in a first direction about a first axis extending in a substantially radial direction from the stored position to the blocking position, and such that the second flap rotates in a second direction about a second axis extending in the substantially radial direction from the stored position to the blocking position, with the first direction being opposite to the second direction.

Abstract: A gas turbine engine for an aircraft. The engine including: an engine core with a turbine, a compressor, a fan located upstream of the compressor and including a plurality of fan blades, and a core shaft connecting the turbine to the compressor; a gearbox which receives an input from the core shaft and outputs drive, via a driveshaft, to the fan so as to drive the fan at a lower rotational speed than the turbine, the drive shaft and core shaft forming a shaft system.

Abstract: A turbofan engine nacelle includes a thrust reverser system provided with at least one movable cowl retracting towards a rear reverse-jet position, tilting pivoting flaps which at least partially close an annular flow duct, and opening lateral openings of this annular flow duct equipped with reverser grids. Each movable cowl includes a control sector that slides in a transverse plane, a deflection device linking a fixed part of the nacelle to this control sector in order to make it slide towards a reversal position when the movable cowl retracts, and flap connecting rods linking this control sector to the pivoting flaps, which tilt these flaps, closing the annular flow duct, when the control sector slides towards its reversal position.

Abstract: A thrust reverser may include a frame, an actuation arrangement, a reverser door pivotally coupled to the frame, and a deployable fairing pivotally coupled to the frame, wherein the deployable fairing is configured to move away from a central axis of the thrust reverser to provide clearance for one of more thrust reverser pivot doors to rotate into a deployed position.

Abstract: A thrust reverser is described that comprises a new type of locking means for locking an actuator in position so that maintenance can be performed on the machine. The locking means comprises a removable locking device for preventing movement of an actuator. The locking means may also function in one configuration as an end cap. An actuator is also described comprising a removable torque limiting device for limiting torque of the actuator.

Abstract: An engine pylon of an aircraft having a rear portion, two rear cowls around the rear portion, each rear cowl having an upper fixed cowl and a lower movable cowl mounted articulated on the rear portion, wherein in the closed position the two lower movable cowls are moved close to one another, such that their lower edges are contiguous, wherein in the open position the two lower movable cowls are tilted such that their lower edges are moved away from one another, for each lower movable cowl, a hinge system fixed between the lower movable cowl and the rear portion, and at least one locking system which locks the two lower movable cowls to one another in the closed position. The presence of the lower movable cowls ensures, among other things, easy access to the interior of the engine pylon.

Abstract: A secondary air system (SAS) of an aircraft engine that produces secondary airflow from a source of secondary air includes a hollow strut and one or more SAS feed pipes upstream thereof. The hollow strut extends radially through the main gas path of the engine and defines therein a strut conduit extending between a strut inlet and a strut outlet at opposite ends of the hollow strut. The strut outlet is in fluid flow communication with a buffer cavity for feeding the secondary airflow to the engine core. The SAS feed pipe includes an inlet receiving the secondary airflow from the source of secondary air, and an outlet in fluid flow communication with the strut inlet to feed the secondary airflow into the strut conduit. The SAS feed pipe has a sonic orifice therein, between the inlet and the outlet thereof.

Abstract: A cascade type thrust reverser device for a turbomachine of an aircraft, comprising a thrust reverser cascade and a casing, the cascade including first cavities, and the casing comprising an opening defining a housing wherein said cascade can be inserted in a first direction, and the casing and said cascade being in relative translation with respect to one another in the first direction between a first position of the device in which the cascade is entirely positioned in the housing and a second position of the device in which said cascade is at least partially outside said housing. The casing comprises an acoustic treatment panel including second cavities extending in a second plane parallel to the first plane, each first cavity facing a second cavity when the device is in the first position to form an acoustic treatment cell.